激波管风洞中叶栅测压实验与计算研究  

SHOCK WIND TUNNEL EXPERIMENTS AND COMPUTATIONAL RESULTS ABOUT TURBINE CASCADE'S AERODYNAMICS CHARACTERISTICS

作　　者：黄海波[1] 季路成[1] 肖翔[1] 李维[1] 徐建中[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100080

出　　处：《工程热物理学报》2002年第3期301-304,共4页Journal of Engineering Thermophysics

基　　金：中国科学院知识创新工程;国家自然科学基金(No.59906012);国家重点基础研究发展规划项目(No.G1999022305

摘　　要：本文利用激波管平面叶栅风洞在四种工况下进行了某叶型叶表压力分布测量实验。该类短周期实验方式的测量精度是值得关注的大问题，为此文中对实验误差及短周期实验测量的合理性进行了分析。继而将实验数据与两种模型下的数值计算结果进行了比较，其中实验结果与按实际情况建立的模型１计算结果吻合。通过实验结果与模型２计算结果比较发现，实验中存在着影响叶栅通道流动周期性的因素，本文仔细分析了该因素可能产生的影响，为今后对该风洞实验段进行改造提供了基础。The static pressure distribution on the surface of a blade was meastired using a shock wind tunnel. The precision of this kind of short-duration tests was especially paid attention. The error and rationality of this kind of measurement were analyzed. Experiments data and computational results using two different models were compared. It is found that the computational results of model 1 that was built according to the real testing configuration agree well with the experimental results. Through the comparison between the experimental data and computational results of model 2, some factors affecting the periodicity of the cascade flow field were found out.

关 键 词：激波管风洞 叶栅流动 测压 风洞实验 

分 类 号：V211.751[航空宇航科学与技术—航空宇航推进理论与工程]